Design method of virtual flight wind tunnel test model

A wind tunnel test and design method technology, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve problems such as difficulty in meeting all requirements, heavy design workload, and difficulty in simultaneously achieving design methods, etc., to reduce The effect of design modification workload and reduction of dependence on design experience
CN112632698APending Publication Date: 2021-04-09CHINA ACAD OF AEROSPACE AERODYNAMICS
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
CHINA ACAD OF AEROSPACE AERODYNAMICS
Publication Date
2021-04-09

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Abstract

The invention discloses a design method of a virtual flight wind tunnel test model. The method comprises the following steps: (1) carrying out parametric modeling by utilizing three-dimensional CAD software according to wind tunnel test basic requirements of scaling, shape, strength, structure and function to obtain a flight wind tunnel test preliminary model; (2) selecting n design parameters from the model weight, the centroid coordinate value and the rotational inertia value, and respectively determining preset target values of the n design parameters; selecting n adjustable feature sizes from the internal space feature size parameters of the flight wind tunnel test preliminary model; and (3) adjusting n adjustable feature sizes by adopting a targeting method in the flight wind tunnel test preliminary model, and calculating n design parameters to enable the n design parameters to be equal to preset target values of the n design parameters. According to the method, the workload of design modification can be greatly reduced, and multiple design values such as the weight value, the rotational inertia value and the centroid coordinate value of the test model can be consistent with target values at the same time.
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Description

technical field

[0001] The invention belongs to the technical field of test aerodynamics, in particular to a design method of a virtual flight wind tunnel test model. Background technique

[0002] Virtual flight wind tunnel test technology is an advanced wind tunnel test and flight performance evaluation technology. During the test, the scaled model of the aircraft research object can perform a certain range of multi-degree-of-freedom movements in the wind tunnel, and the specific degrees of freedom and movement range are related to the experimental research content. In the test, the test model is subjected to corresponding aerodynamic and dynamic effects in the flight environment simulated by the wind tunnel and the current flight state, and these two effects are also interacted and coupled. Under the joint coupling effect of aerodynamic force and dynamics, the attitude change of the test model within the allowable range can be measured and collected by the measurement sys...

Claims

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